基于FFD方法的高超声速升力体气动优化  

Aerodynamic optimization of hypersonic lifting body based on FFD method

作　　者：夏陈超 邵纯[1] 姜婷婷[1] 陈伟芳[1] 

机构地区：[1]浙江大学航空航天学院,杭州310027

出　　处：《固体火箭技术》2015年第6期751-756,共6页Journal of Solid Rocket Technology

基　　金：国家重点基础研究发展计划(2014CB340201)

摘　　要：将FFD(Free Form Deformation)自由变形法与无限插值动网格方法相结合,发展了一种飞行器参数化建模和网格生成方法。二维和三维的实例显示自由变形之后得到的飞行器几何外形及其对应的网格能保持平滑光顺,验证了方法的有效性。在此基础上,结合径向基函数代理模型和CFD技术发展了一套优化设计方法并对高超声速升力体外形进行了气动优化。基于自适应模拟退火算法的单目标优化表明,在保持原有外形体积不减小的情况下,升阻比提高了1.28%;基于NSGA-II的多目标优化得到了飞行器升阻比和体积的最优解集,典型优化外形的升阻比和体积分别提高了2.93%和2.49%。升力体的优化结果表明了FFD方法的有效性和优化设计方法的实用性。A general method of parametric modeling and grid generation was developed by combining the free form deformation （FFD） and transfinite interpolation techniques.Smoothness of geometry shape and satisfactory quality of grid were achieved from two-and three-dimensional cases.An optimization framework was then constructed by adopting a surrogate model and optimization al- gorithms.The aerodynamic shape optimization of a hypersonic lifting body was utilized as a demonstration case for the developed framework.The result of single objective optimization using adaptive simulated annealing algorithm shows that the lift-drag ratio has an increase of 1.28% with a constraint on the volume. Besides, multi-objective optimization is carried out by using NSGA-II algo- rithm, and the Pareto solutions about volume and lift-drag ratio are obtained. One of the typical solutions on the Pareto front shows that the lift-drag ratio has an increase of 2.93% and the volume has an increase of 2.49%.Optimization of the lifting body in this work shows the usability of the free form deformation technique and the good practicality of the optimization framework.

关 键 词：自由变形 无限插值法 高超声速 升力体 优化设计 

分 类 号：V441[航空宇航科学与技术—飞行器设计]